EP2946094B1 - Écran thermique pour réducteur de moteur à turbine à gaz et procédé de réduction du transfert de chaleur à un tel réducteur - Google Patents

Écran thermique pour réducteur de moteur à turbine à gaz et procédé de réduction du transfert de chaleur à un tel réducteur Download PDF

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Publication number
EP2946094B1
EP2946094B1 EP13871712.9A EP13871712A EP2946094B1 EP 2946094 B1 EP2946094 B1 EP 2946094B1 EP 13871712 A EP13871712 A EP 13871712A EP 2946094 B1 EP2946094 B1 EP 2946094B1
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EP
European Patent Office
Prior art keywords
gearbox
heat shield
engine
gas turbine
leg
Prior art date
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Active
Application number
EP13871712.9A
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German (de)
English (en)
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EP2946094A1 (fr
EP2946094A4 (fr
Inventor
Timothy Webb
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
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United Technologies Corp
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Filing date
Publication date
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Publication of EP2946094A4 publication Critical patent/EP2946094A4/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0412—Cooling or heating; Control of temperature
    • F16H57/0415—Air cooling or ventilation; Heat exchangers; Thermal insulations
    • F16H57/0419—Thermal insulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49828—Progressively advancing of work assembly station or assembled portion of work

Definitions

  • the present disclosure generally relates to gas turbine engines and, more specifically, to heat shields for gearboxes of gas turbine engines.
  • a gas turbine engine typically used as a source of propulsion in aircraft, operates by drawing in ambient air, combusting that air with a fuel, and then forcing the exhaust from the combustion process out of the engine.
  • a gas turbine engine has a case surrounding the core components, such as a diffuser case surrounding a diffuser and combustor.
  • An auxiliary gearbox is generally positioned near this diffuser case and in mechanical communication with the fan, compressor, and/or turbine.
  • the combustor produces copious amounts of heat, some of which is transferred to the diffuser case and then transferred to the gearbox. Such heat can be detrimental to the operation and life of the gearbox. Specifically, the heat may cause any lubricant working in the gearbox to coke or components of the gearbox may be damaged due to heat stress.
  • cooling is typically provided to the auxiliary gearbox in the form of compressed air from the compressor, a fuel working as a coolant, or a dedicated coolant in addition to any cooling provided by a lubricant acting on the gearbox. While effective, such cooling requires extra components to communicate these fluids through the engine and, in the case of the dedicated coolant, may require additional equipment to remove heat from the coolant. These additional components and equipment increase the weight and size of the engine, as well as the maintenance needed to keep the engine operating.
  • US 2010/180568 A1 discloses a heat shield positioned in an aft cone of a turbofan to protect a gear box and power takeoff shafts.
  • the present invention provides a combination of a heat shield for a gearbox of a gas turbine engine and the gearbox, according to claim 1.
  • a combination of a heat shield for a gearbox of a gas turbine engine and the gearbox therefore is disclosed.
  • the heat shield includes a barrier adapted to be positioned between the gas turbine engine and the gearbox, with the barrier being complementarily shaped to the shape of the gearbox.
  • a plurality of connectors mount the heat shield to the gearbox.
  • the heat shield includes a thermal insulation core and a metal sheet surrounding the thermal insulation core.
  • each connector may be welded to the barrier.
  • each connector may be bolted to the gearbox.
  • the barrier may include a body having a longitudinal axis.
  • the heat shield may also have a first leg extending from the body in a first direction perpendicular to the longitudinal axis and forming a first angle between the body and first leg.
  • the heat shield may further include a second leg extending from the body in a second direction opposite to the first direction and forming a second angle between the body and the second leg.
  • the heat shield may further include a foot extending from the second leg in the second direction and forming a third angle between the second leg and the foot.
  • the second angle may be greater than the first angle.
  • the metal sheet may be chromium nickel stainless steel.
  • the insulation core may be low-conductivity fiber felt insulation.
  • a gas turbine engine may include a gearbox operatively associated with the engine and a heat shield formed to the shape of the gearbox.
  • the gearbox may be mounted outside an engine core component.
  • the heat shield may be mounted to the gearbox by a plurality of connectors between the gearbox and the engine core component.
  • the heat shield may include a thermal insulation core and a metal sheet surrounding the thermal insulation core.
  • the engine core component may be one of the compressor, combustor, and turbine.
  • the gas turbine engine may further include a diffuser between the compressor and the combustor and a diffuser case surrounding the diffuser and combustor.
  • the gearbox may be positioned around the diffuser case and the heat shield may be positioned between the gearbox and diffuser case.
  • the heat shield may include a body, a first leg extending from the body in a circumferential direction around the diffuser case, and a second leg extending from the body away from the diffuser case.
  • the heat shield may further include a foot extending from the second leg away from the diffuser case.
  • each connector may be welded to the heat shield and bolted to the gearbox.
  • the present invention provides a method of limiting an amount of heat transferred to a gearbox of a gas turbine engine, according to claim 11.
  • the method includes aligning a heat shield with a gearbox such that the shape of the heat shield is complementary with the shape of the gearbox.
  • the method further includes mounting the heat shield to the gearbox and mounting the gearbox to the engine such that the heat shield is positioned between the gearbox and the engine.
  • the method may further include welding a plurality of connectors to the heat shield prior to mounting the heat shield to the gearbox.
  • the mounting of the heat shield to the gearbox may include bolting the heat shield to the gearbox.
  • the aligning of the heat shield with the gearbox may further include positioning the heat shield such that all surfaces of the gearbox which will face the engine are covered by the heat shield.
  • a gas turbine engine is depicted and generally referred to by the numeral 20. While the engine 20 of FIG. 1 is depicted as a turbofan type of gas turbine engine for an aircraft, it should be understood that this is in no way limiting, and is only provided for ease of illustration. The teachings of the present disclosure apply to any other form of gas turbine engine is possible as well. Further, as the structure and function of a gas turbine engine 20 and well known in the art, no description except that which is necessary to sufficiently describe the present invention will be given.
  • the engine 20 is depicted in FIG. 1 as including a plurality of components axially aligned along central axis 22. Such components include a fan 24, a dual-spool compressor 26 downstream from the fan 24, a diffuser 28 communicating between the compressor 26 and a combustor 30 downstream from the compressor 26, and a dual-spool turbine 32 downstream from the combustor 30. As used herein, "downstream" means further along the flow of air through the engine 20.
  • the engine 20 of FIG. 1 is depicted as a dual-spool engine, it is to be understood that any configuration is possible, such as, but not limited to, single or triple spool configurations.
  • the engine 20 further includes casings surrounding the above-mentioned engine components as well as other components. Specifically, a fan case 34 surrounds the fan 24 and a portion of the compressor 26, a compressor case 36 surrounds the compressor 26, a diffuser case 38 surrounds the diffuser 28 and combustor 30, and a turbine case 40 surrounds the turbine 32.
  • many external components of the engine 20 are mounted to the engine casings, such as, but not limited to, a fuel supply, an oil supply, or a gearbox 42.
  • this gearbox 42 is driven by an engine shaft that mechanically transfers rotational energy from the turbine 32 to the gearbox 42.
  • the gearbox 42 then drives the accessories of the engine 20 such as, but not limited to, a fuel pump or an oil pump.
  • the gearbox 42 may be mounted directly to the diffuser case 38. While this is typical of gas turbine engines used in aerospace applications, the present disclosure drastically departs from the prior art by providing a heat shield 44 between the gearbox 42 and diffuser case 38.
  • the heat shield 44 is provided to limit the amount of heat transferred to the gearbox 42 from internal engine components, such as, but not limited to, the combustor 30.
  • a lubrication system providing lubricant to the gearbox 42, there is no need for a dedicated cooling system as mentioned above, which would otherwise add to the weight and complexity of the system.
  • the heat shield 44 may consist of a thermal insulation core 50 flanked by a metal sheet 51 on both sides to collectively form a barrier 52 as shown in FIG. 3 .
  • the thermal insulation core 50 may be manufactured from many different materials including, but not limited to, low-conductivity fiber felt insulation.
  • the insulator may be pliable or rigid.
  • the insulation used to form the core 50 can continuously withstand up to about 2000 degrees Fahrenheit.
  • the metal sheet 51 it may be manufactured from many different metals including, but not limited to, chromium-nickel stainless steel sheet with titanium.
  • the metal sheet 51 can continuously withstand up to about 1500 degrees Fahrenheit. Examples of suitable material for the metal sheet 51 include AMS5510 and Type 321 stainless steel, although other materials are possible.
  • the thermal insulation core 50 and metal sheet 51 may be modified to withstand other temperatures as needed by varying the density of the materials used, or by changing the materials used all together, and should not be limited by the embodiments presented herein.
  • the heat shield 44 may be mounted to the gearbox 42 by a plurality of connectors 53.
  • the connectors 53 are brackets spot welded to the heat shield 44 and bolted to the gearbox 42.
  • the connectors 53 are welded to a hot surface 48 of the heat shield 44, which is the surface of the heat shield 44 facing the diffuser case 38. Having the heat shield 44 bolted to the gearbox 42 via the connectors 53 maintains the heat shield 44 in a fixed position, while still allowing the heat shield 44 to be removed when maintenance to the gearbox 42 is needed, or to allow the heat shield 44 to be replaced should the heat shield 44 become damaged in some way.
  • the embodiment presented in FIG. 2 is only one mode of attaching the heat shield 44 to the gearbox 42. Other modes of attachment are also possible such as, but not limited to, welding of the connectors 46 to both the gearbox 42 and the heat shield 44.
  • the heat shield 44 of FIG. 2 be manufactured as thinly as possible, while still providing the necessary barrier to heat transfer.
  • the total thickness of the heat shield 44, thickness A-A may be up to about 0.250 inches.
  • each sheet 52 may have a thickness B-B of about 0.004 inches, while the thermal insulation core 50 may have a thickness C-C of up to about 0.241 inches.
  • the thicknesses A-A, B-B, C-C depicted FIG. 3 are only representative of one embodiment of the present disclosure, and may each be modified provided there is sufficient space for any increased thicknesses, and any decreased thicknesses still provide the desired heat insulation.
  • the heat shield 44 may be formed complementarily to the shape of the gearbox 42, such as in the case of the heat shield 44 of FIGS. 4 and 5 . As shown, in so doing, the presented heat shield 44 protects all surfaces of the gearbox 42 which are oriented towards the diffuser case 38.
  • the shape of the gearbox 42 of FIG. 4 as an example, it can be seen in FIG. 5 , that the formed heat shield 44 matches the shape of the gearbox 42.
  • the heat shield 44 may include four sections as will now be described.
  • the four sections of the heat shield 44 include a body 54 extending along a longitudinal axis 55.
  • a second section which is a first leg 56, extends primarily in a first direction 58 from the body to form a first angle ⁇ between the first leg 56 and the body 54.
  • the first direction 58 is oriented substantially perpendicular to the longitudinal axis 55.
  • a third section which is a second leg 60, extends from the body 54 in a second direction 62, where the second direction 62 is opposite to the first direction 58. In so doing, a second angle ⁇ is formed between the body 52 and the second leg 60.
  • the fourth section which is a foot 64, extends from the second leg 60 in the second direction 62 to form a third angle ⁇ between the second leg 60 and the foot 64. As depicted in FIG. 5 , all angles ⁇ , ⁇ , ⁇ are greater than ninety degrees and the second angle ⁇ is greater than the first and third angles ⁇ , ⁇ .
  • the body 54 of the heat shield 44 is oriented tangentially to the diffuser case 38.
  • the first leg 56 extends from the body 53 in a circumferential direction around the diffuser case 38 and the second leg 60 extends from the body 53 away from the diffuser case 38.
  • the foot 64 extends from the second leg 60 away from the diffuser case 38 in a radial direction with respect to the central axis 22.
  • the engine 20, gearbox 42, and the heat shield 44 may be configured together by first aligning the heat shield 44 with the gearbox 42. Specifically for the gearbox 42 and heat shield 44 illustrated in FIGS. 2 and 4 , the heat shield is aligned such that the shape of the heat shield 44 is complementary with the shape of the gearbox 42. Such an alignment of the heat shield 44 with the gearbox 42 will allow the heat shield 44 to cover all surfaces of the gearbox 44 that face the engine 20.
  • the heat shield 42 is then mounted to the gearbox 44. This may be accomplished by bolting the heat shield 42, or bolting a plurality of connectors 53 that have been welded to the heat shield 44, to the gearbox 44. Once the heat shield 42 has been mounted to the gearbox 44, the gearbox 44 is mounted to the engine 20 such that the heat shield is positioned between the gearbox 44 and the engine 20.
  • the heat shield disclosed herein has applicability in a variety of settings such as, but not limited to, reducing heat stress on external engine components of a gas turbine engine, specifically for a gearbox mounted to the diffuser case of a gas turbine engine.
  • a heat shield in combination with a typical lubrication system does not require a dedicated coolant or any of the equipment associated with a dedicated coolant to cool the gearbox.
  • the presented heat shield does not impose upon the strict size and weight limitations to which gas turbine engines abide when utilized in conjunction with aircraft.
  • the shield is relatively thin and may be formed to the shape of the gearbox further reducing the geometric envelope of the heat shield.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (14)

  1. Combinaison d'un écran thermique (44) pour un réducteur (42) d'un moteur à turbine à gaz et donc le réducteur (42), l'écran thermique (44) comprenant :
    une barrière (52) conçue pour être positionnée entre le moteur à turbine à gaz et le réducteur (42), la barrière (52) étant de forme complémentaire à la forme du réducteur (42) ; et
    une pluralité de connecteurs (53, 46) montant l'écran thermique (44) sur le réducteur (42), dans laquelle l'écran thermique (44) comprend un noyau d'isolation thermique (50) et une feuille métallique (51) entourant le noyau d'isolation thermique (50).
  2. Écran thermique (44) et réducteur (42) selon la revendication 1, dans lesquels chaque connecteur (53, 46) est soudé à la barrière.
  3. Écran thermique (44) et réducteur (42) selon la revendication 2, dans lesquels chaque connecteur (53) est boulonné au réducteur (42) .
  4. Écran thermique (44) et réducteur (42) selon la revendication 1, dans lesquels la barrière (52) inclut un corps (54) ayant un axe longitudinal (55), une première patte (56) s'étendant depuis le corps (54) dans une première direction (58) perpendiculaire à l'axe longitudinal (55) et formant un premier angle (α) entre le corps (54) et la première patte (56), et une seconde patte (60) s'étendant depuis le corps (54) dans une seconde direction (62) opposée à la première direction (58) et formant un deuxième angle (β) entre le corps (54) et la seconde patte (60).
  5. Écran thermique (44) et réducteur (42) selon la revendication 4, dans lesquels l'écran thermique (44) inclut en outre un pied (64) s'étendant depuis la seconde patte (60) dans la seconde direction (62) formant un troisième angle (γ) entre la seconde patte (60) et le pied (64) .
  6. Écran thermique (44) et réducteur (42) selon la revendication 4, dans lesquels le deuxième angle (β) est supérieur au premier angle (α) .
  7. Écran thermique (44) et réducteur (42) selon la revendication 1, dans lesquels le noyau d'isolation (50) est un isolant en feutre de fibres à faible conductivité.
  8. Moteur à turbine à gaz (20), comprenant :
    l'écran thermique (44) et le réducteur (42) selon l'une quelconque des revendications précédentes, dans lequel le réducteur (42) est associé de manière opérationnelle au moteur (20) et monté à l'extérieur d'un composant de noyau de moteur ; et
    dans lequel l'écran thermique (44) est positionné entre le réducteur (42) et ledit composant de noyau.
  9. Moteur à turbine à gaz (20) selon la revendication 8, comprenant en outre un diffuseur (28) entre le compresseur (26) et la chambre de combustion (30), et un boîtier de diffuseur (38) entourant le diffuseur (28) et la chambre de combustion (30), le réducteur (42) étant positionné autour du boîtier de diffuseur (38) et l'écran thermique (44) étant positionné entre le réducteur (42) et le boîtier de diffuseur (38).
  10. Moteur à turbine à gaz (20) selon la revendication 9, dans lequel l'écran thermique (44) inclut un corps (54), une première patte (56) s'étendant depuis le corps (54) dans une direction circonférentielle autour du boîtier de diffuseur (38), et une seconde patte (60) s'étendant depuis le corps (54) à l'opposé du boîtier de diffuseur (38).
  11. Procédé de réduction d'une quantité de chaleur transférée à un réducteur (42) d'un moteur à turbine à gaz (20), comprenant :
    l'alignement d'un écran thermique (44) avec un réducteur (42) de sorte que la forme de l'écran thermique (44) est complémentaire à la forme du réducteur (42), dans lequel l'écran thermique (44) comprend un noyau d'isolation thermique (50) et une feuille métallique (51) entourant le noyau d'isolation thermique (50) ;
    le montage de l'écran thermique (44) sur le réducteur (42) ; et
    le montage du réducteur (42) sur le moteur (20), dans lequel l'écran thermique (44) est positionné entre le réducteur (42) et le moteur (20) .
  12. Procédé selon la revendication 11, comprenant en outre le soudage d'une pluralité de connecteurs (53, 46) à l'écran thermique (44) avant le montage de l'écran thermique (44) sur le réducteur (42) .
  13. Procédé selon la revendication 11, dans lequel le montage de l'écran thermique (44) sur le réducteur (42) comprend le boulonnage de l'écran thermique (44) sur le réducteur (42).
  14. Procédé selon la revendication 11, dans lequel l'alignement de l'écran thermique (44) du réducteur (42) comprend le positionnement de l'écran thermique (44) de sorte que toutes les surfaces du réducteur (42) qui feront face au moteur (20) sont recouvertes par l'écran thermique (44).
EP13871712.9A 2013-01-16 2013-01-16 Écran thermique pour réducteur de moteur à turbine à gaz et procédé de réduction du transfert de chaleur à un tel réducteur Active EP2946094B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2013/021659 WO2014112988A1 (fr) 2013-01-16 2013-01-16 Écran thermique pour réducteur de moteur à turbine à gaz

Publications (3)

Publication Number Publication Date
EP2946094A1 EP2946094A1 (fr) 2015-11-25
EP2946094A4 EP2946094A4 (fr) 2016-07-27
EP2946094B1 true EP2946094B1 (fr) 2019-05-22

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US (1) US10145306B2 (fr)
EP (1) EP2946094B1 (fr)
WO (1) WO2014112988A1 (fr)

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GB201716499D0 (en) 2017-10-09 2017-11-22 Rolls Royce Plc Gas turbine engine fireproofing
GB201804397D0 (en) * 2018-03-20 2018-05-02 Rolls Royce Plc Gas turbine engine heatshield
GB201804398D0 (en) * 2018-03-20 2018-05-02 Rolls Royce Plc Gas turbine engine heatshield

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GB1127659A (en) * 1966-09-16 1968-09-18 Rolls Royce Improvements in gas turbine engines
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US6170252B1 (en) * 1998-12-14 2001-01-09 United Technologies Corporation Locator for a gearbox mount
FR2882573B1 (fr) * 2005-02-25 2007-04-13 Snecma Moteurs Sa Carter interne de turbomachine equipe d'un bouclier thermique
US20090129967A1 (en) * 2007-11-09 2009-05-21 General Electric Company Forged austenitic stainless steel alloy components and method therefor
US8192143B2 (en) 2008-05-21 2012-06-05 United Technologies Corporation Gearbox assembly
US20100180568A1 (en) 2009-01-22 2010-07-22 Sachs Humberto W Heat regeneration for a turbofan, a Velarus Propulsion
US20110239660A1 (en) * 2010-03-30 2011-10-06 United Technologies Corporation Mounting arrangement for gas turbine engine accessories and gearbox therefor
US8490410B2 (en) 2010-11-17 2013-07-23 United Technologies Corporation Axial accessory gearbox
GB2490348B (en) * 2011-04-28 2013-12-25 Rolls Royce Plc A head part of an annular combustion chamber
US9500133B2 (en) 2012-12-23 2016-11-22 United Technologies Corporation Mount with an axial upstream linkage for connecting a gearbox to a turbine engine case
CN203210184U (zh) * 2013-03-12 2013-09-25 浙江大宇电器有限公司 一种磨光机齿轮箱隔热罩

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Publication number Publication date
EP2946094A1 (fr) 2015-11-25
EP2946094A4 (fr) 2016-07-27
WO2014112988A1 (fr) 2014-07-24
US10145306B2 (en) 2018-12-04
US20150361898A1 (en) 2015-12-17

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